Portable pre-fabricated airplane hangar

ABSTRACT

Portable apparatus for shelter and protection of small airplanes which may be utilized with standardized mooring ring arrays existing at small craft mooring areas of airports. The apparatus is of inexpensive, light-weight pre-fabricated design such that it is capable of rapid assembly and disassembly, ease of transport, yet sturdy weather-resistant stability; the components of the pre-fabricated structure are constructed along essentially planar design with rectangular/parallel bracing, and in assembled form they constitute a main housing for receiving the fuselage of the airplane and oppositely extending wing coverage nacelles extending on each side of the main housing in position to receive the wings of the airplane. The structure is readily adaptable to receive any of the many types of small aircraft or it may be converted with aid of special accessory structure to receive the larger twin engine aircraft.

United States Patent [191 Pierce [4 June 25, 1974 PORTABLE PRE-FABRICATED AIRPLANE HANGAR [76] Inventor: Alvin S. Pierce, 6614 McGee,

Wheatland, Okla. 73097 [22] Filed: May 22, 1972 [21] Appl. No.: 255,576

[52] US. Cl. 52/23, 52/73 [51] Int. Cl E04b 5/43 [58] Field of Search 52/236, 731, 79, 3-5, 52/23, 143

[56] References Cited UNITED STATES PATENTS 2,511,974 6/1950 Finken 52/148 2,816,330 12/1957 Sherron 52/73 2,820,991 1/1958 Poole 52/73 2,992,709 7/1961 McIntosh 52/73 3,074,518 1/1963 Conrad 52/73 3,150,641 9/1964 Kesh 52/3 3,449,874 6/1969 Beaapre 52/23 3,550,333 12/1970 Kliewer 52/73 3,708,200 1/1973 Richards 52/64 FOREIGN PATENTS OR APPLICATIONS 423,196 4/1911 France 52/143 174,083 8/1965 U.S.S.R.......... 52/73 768,344 10/1967 Canada 52/79 711,338 9/1931 France 52/4 OTHER PUBLICATIONS House & Home, Sept. 1956, p. 134.

Primary ExaminerHenry C. Sutherland Assistant Examiner-Henry E. Raduazo Attorney, Agent, or FirmDunlap, Laney, Hessin, Dougherty [5 7] ABSTRACT Portable apparatus for shelter and protection of small airplanes which may be utilized with standardized mooring ring arrays existing at small craft mooring areas of airports. The apparatus is of inexpensive. light-weight pre-fabricated design such that it is capable of rapid assembly and disassembly, ease of transport, yet sturdy weather-resistant stability; the components of the pre-fabricated structure are constructed along essentially planar design with rectangular/parallel bracing, and in assembled form they constitute a main housing for receiving the fuselage of the airplane and oppositely extending wing coverage nacelles extending on each side of the main housing in position to receive the wings of the airplane. The structure is readily adaptable to receive any of the many types of small aircraft or it may be converted with aid of special accessory structure to receive the larger twin engine aircraft.

PORTABLE PRE-FABRICATED AIRPLANE HANGAR BACKGROUND OF THE INVENTION 1. Field of the Invention The invention relates generally to aircraft hangars and, more particularly, but not by way of limitation, it relates to a standardized form of pre-fabricated aircraft hangar which can be utilized with existing mooring rings.

2. Description of the Prior Art The prior art includes various types of buildings and shelters which are utilized in providing aircraft protection against the adverse effects of weather. Provision of aircraft shelter has traditionally been an expensive and troublesome undertaking due to the fact that airplanes are inherently of a shape which requires large storage areas incapable of efficient utilization of space, and the fact that there is not a large consumer demand which would tend to diminish and stabilize costs connected with such storage protection. Some of the recent prior art has been directed to solution of the problem through unique design of building structures, overhead shelters, adaptable mobile home type structures and the like; however, such efforts have generally been directed to establishment of more permanent, heavy and expensive structures and considerations as to side-byside storage of pluralities of small craft, as necessitated by the problems of providing sufficient mooring areas at small craft airports.

SUMMARY OF THE INVENTION The present invention contemplates a portable prefabricated airplane hangar which provides total coverage of the airplane while being secured to existing mooring rings. In a more limited aspect, the invention consists of a pre-fabricated main housing structure receiving the fuselage of the airplane therein, and which main housing supports wing protection nacelles extending on each side thereof for receiving the outer wing portions of the airplane. The pre-fabricated structure is characterized by generally planar construction with all parts assembled through use of rapid connecting fasteners, and the planar structure is securely positionable on the ground by cable connection to existing mooring rings. The basic hangar structure provides the basic weather protection necessary for the more moderate temperature weather zones, but additional structure is readily adaptable for total protection in colder and/or high wind regions.

Therefore, it is an object of the present invention to provide a small aircraft hangar which is inexpensive yet offers a high degree of stability and protection against the elements.

It is also an object of the invention to provide an aircraft hangar apparatus which is readily transportable and can be rapidly positioned and assembled.

It is yet another object of the present invention to provide a light-weight, low cost airplane hangar which can readily be made available to fulfill the need of numerous small aircraft owners.

Finally, it is an object of the present invention to provide a low cost small aircraft hangar having high stability to wind disturbance while providing aircraft protection within a minimum of ramp or surface area.

Other objects and advantages of the invention will be evident from the following detailed description when read in conjunction with the accompanying drawings which illustrate the invention.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a top plan view of the airplane hangar of the present invention;

FIG. 2 is a side elevation of the airplane hangar constructed in accordance with the present invention;

FIG. 3 is a front view of the airplane hangar of FIGS. 1 and 2;

FIG. 4 is a plan view of a main housing side panel;

FIG. 5 is an elevational plan view of a main housing rear panel section;

FIG. 6 is a sectional view illustrating the method of joinder of main housing roof sections and side panels;

FIG. 7 is a bottom view of a portion of a roof section;

FIG. 8 is a sectional view illustrating the method of joinder between sidepanels and roof sections;

FIG. 9 is a front elevational view of a wing cover nacelle;

FIG. 10 is a sectional view of a wing cover nacelle including forward door panel;

FIG. 11 is an elevational plan view of an alternative form of side panel for use with low wing type aircraft;

as designed for specific forms of small aircraft having wing tanks.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT FIGS. 1, 2 and 3 illustrate the basic form of a hangar 10 as employed for protective shelter of small aircraft. The general class of single engine monoplanes is sufficiently standardized in size, as to heighth, wing span and fuselage length, that one size of hangar 10 can be employed economically for all such craft. Hangar 10 is depicted in FIGS. 1-3 as housing a Cessna Model 182 aircraft but hangar 10 is adaptable for all small craft either high wing or low wing types, and the basic structure is readily adaptable for enlargement and shelter of larger craft, as will be further described below.

Hangar 10 consists of a main housing 12 which is comprised of roof sections 14 and 16 as secured along ridgeline l8, and the roof sections are supported by uniform side walls 20 and 22 and an end wall 24, particular construction and fastening techniques to be further described below.

A pair of wing cover nacelles 26 and 28 are secured to each of respective side panels 20 and 22 to provide extended housing covering the outer wing portions of the aircraft. Each of wing cover nacelles 26 and 28 includes an upward swinging forward door panel 30 and 32, respectively, as will be further described. Hangar 10 may be positioned over and secured by the use of the conventional triangular array mooring rings 34, 36

and 38 as are existent at most small craft airports. In the event that mooring rings are not present or that hangar is used at a private airstrip, conventional screw-type mooring rods of sufficient length and screw pitch may be employed.

After initial fastener assembly of roof 12 to side panels and 22 and end wall 24, rear cables and 42 may be secured from respective corner eyes 44 and 46 to the rear mooring eye 34. In like manner, the hangar right side is secured by connection of cables 48, 50, 52 and 54 from respective cable eyes 56, 58, and 62 to the mooring ring 38. The left side is similarly secured by quadrature arrayed cables, cables 64 and 66 from cable eyes 68 and 70 being shown connected to the mooring ring 36. The various anchoring cables may be made taut by use of such as turnbuckle linkages or the like. Also, one or more cables 72 may be connected across main housing 12 at the ground level between suitable cable eyes 74 and 76. In practice, it has been found that two such cables 72 disposed transversely across main housing 12 at each of forward and rearward locations of wing cover nacelles 26 and 28 function to good advantage (See FIG. 1).

The side walls 22 and 20 are pre-fabricated as left and right pairs each comprised of the identical framing structure as externally covered by a laminate covering. Thus, referring to FIG. 4, the left side panel 20 consists of essentially wooden framing as covered entirely by a laminate cover 82 which in present designs consists of woven rovings impregnated with polyester resin. An upper longitudinal frame member 84 is made up of a forward frame member 86 (1 inch by 8 inch wood plank) longitudinally secured to a rearward frame member 88 (1 inch by 4 inch wood plank) while a wing frame member 90 provides supporting strength for the wing cover nacelle 26 (FIG. 1). A spacer block 92 of such as /1 inch plywood is secured between forward frame member 86 and wing frame member 90 to provide further support. Skeletal framing is provided by a base frame member 94 and longitudinal frame members 96 and 98 in coaction with a plurality of vertical frame members 100. The frame members 94, 96, 98 and 100 may consist of 3 1 inch by 4 inch wood framing as presently designed, and conventional fastening techniques are employed. A plurality of X-braces 102, e.g. 74 inch by 2 inch plywood laminated with woven rovings, are employed for transverse bracing within each frame section.

A plurality of cord washers 104 are suitably secured at spaced positions along the underside of base frame member 94. Cord washers 104, or any suitable form of resilient cushioning member, provide even ground contact as well as vibration damping (during high wind) to the assembled hangar 10. The entire outer surface of side walls 20 and 22 are covered with laminate cover 82 which, as previously stated, may be a woven rovings laminate; however, a better grade laminate 0ffering a more high quality finish may also be employed for those desiring a more appealing exterior appearance.

FIG. 5 illustrates a half-section 106 of rear end wall 24 (FIG. 3). End wall 24 utilizes two such half-sections 106 of identical framing, except laminated on opposite sides, to form the exterior surface. Thus, showing a right side half-section 106, the section consists of vertical frame members 108 and 110 as rigidly fastened to upper and lower horizontal frame members 112 and 114, respectively, as transversely strengthened by X- bracing members 116. The vertical and horizontal frame members 108-114 may each consist of 1 inch by 4 inch white pine as secured by conventional fasteners, and X-braced members 116 again may consist of A inch by 2 inch plywood laminated with woven rovings.

The end frame half-section 106 is covered by the exterior cover or laminate 118 extending from lower horizontal frame member 114 upward to the peak of the roof. A notch 120 is formed for mating engagement with a roof ridge frame section (as will be further described), and a side portion 122 of end wall half-section 106 extends outward to provide fastening surface to the respective side wall, as shown within dashed-lines 124. Fastening of end wall portion 122 to the side wall is carried out by conventional means and a plurality of bolts 126, e.g. quarter inch by 3 inch hex head bolt and nuts, provide juxtaposition securing of two half-sections to form a complete end wall 24. Once again, rubber cord washers 104 are periodically disposed along the underside of lower horizontal frame member 114.

FIG. 6 illustrates the manner in which roof sections 14 and 16 are constructed. The roof sections 14 and 16 are symmetrical and interchangeable as between usage in either left side or right side positions. Referring to roof section 14, the essential construction and framing consists of longitudinal frame members and 132 as secured by a plurality of transverse frame members 134. FIG. 6 illustrates the construction wherein a plurality of transverse frame members 134, as disposed at pre-determined spacing, are secured to longitudinal frame member 132. A plurality of X-brace members 136 are then disposed between each successive ones of transverse frame member 134 to provide suitable cross bracing.

The ridge line horizontal frame member 130 may consist of a beveled 1 inch by 4 inch wood member while the lower horizontal frame member 132 may be a beveled 2 by 4 stringer. The transverse frame members 134 may each be constructed of such as one inch by four inch white pine blanking and X-bracing members 136 may consist of laminated plywood spars. An outer laminate cover 138 is then bonded over all external surfaces and into integral or bonded contact with the individual framing members.

Referring again to FIG. 6, each of roof sections 14 and 16 are identical in construction and are joined along ridge line 18 by securing ridge line longitudinal frame member 130 together by suitable fastening, e.g. bolts 140 periodically spaced along ridge line 18. Also, transverse braces 142 are secured between selected pairs of transverse frame 134, with suitable fastening, e.g. by nail or bolt, to insure proper ridge line angle as between roof sections 14 and 16. i

The outer edges of roof sections 14 and 16 are joined to their respective side walls as, for example, by joinder of roof section longitudinal member 132 on top of upper horizontal frame member 80 of left side wall 20 by suitable fastening, e.g. bolts or the like. Joinder is identical for the opposite side wall connection. FIG. 8 illustrates the manner in which further angular strengthening is afforded by usage of a plurality of gussets 144 as suitably fastened between selected pairs of roof section transverse frame members 134 and side wall vertical frame members 100. The gussets 144 may be formed to be such as molded double laminations of woven rovings, and such strengthening members are specifically utilized for interconnection of those vertical frame members 100 and transverse frame members 134 located fore and aft of the attachment point for wing nacelles 26 and 28. Gussets 144 may be utilized further along the length of roof sections 14 and 16 to enable still greater strength. Also, as shown in FIG. 8, roof sections 14 and 16 may be constructed with an overlapping flap member 146 (as shown in dashedlines) to provide further weather sealing. The flap member 146 may be constructed as a continuance overlapping portion of roof section laminate 138 with suitable framing support.

FIGS. 9 and illustrate construction of the wing cover nacelles 26 and 28 which are similarly constructed in left and right pairs. Referring to FIG. 9, the right wing nacelle 28 consists of an end wall 150 and a joining assembly 152 supporting upper laminated covering 154 and a continuous laminar rear wall 158. A bottom panel 156 may be constructed from suitably laminated sheet plywood. See also the sectional view of FIG. 10, and it should be noted that a front cover door 160 is omitted from a view of FIG. 9. The joining assembly 152 is formed to extend an upper base flange 162 and an offset lower base flange 164 for interconnective securing to the side walls or, specifically, right side wall 22. Thus, the upper base flange 162 is suitably secured to the inside of horizontal frame member 98 of side wall 22, while the lower base flange 164 is secured to the outer side of horizontal frame member 90, thus achieving a cantilever effect. The joining assembly 152 is suitably formed by light plywood framing construction as covered by laminated fiberglas material in coextensive joinder to upper cover surface 154 and lower cover panel 156. The upper cover 154, lower cover panel 156 and rear cover 158 may be formed through conventional practice from molded fiberglass and may utilize plywood and/or stringer bracing and spars. A plurality of cord ribs 166 are formed periodically and longitudinally along both upper cover 154 and lower cover panel 156 by inclusion of suitable formation material within the molded fiberglas panels.

The leading edge of upper cover 154 and lower cover panel 156 include suitable transverse spars 168 and 170, e.g. laminated plywood spar sections. The lower spar 170 carries a plurality of strap hinges 172 which provide pivotal attachment of door panel 160 thereto. Suitable locking fasteners may then be secured along upper spar 168 to provide cover fastenings. The overhang or lower spar 170 also includes a series of apertures 174 through which the laminar lowercover panel 156 may be secured.

In operation, the afore-described individual sections may be assembled in the manner as shown in FIGS. 1, 2 and 3 to provide aircraft cover. Upon assembly of the individual sections, the hangar 10 is then secured to existing mooring rings 34, 36 and 38 by the associated cable connections 48, 50, 64, 66, etc. Upon moving the aircraft into hangar 10, the wing nacelle cover doors 160 are placed in the downward or open position whereupon the aircraft is simply backed into the fuselage housing portion of hangar 10 with the aircraft wings moving within the wing cover nacelles 26 and 28. Cover doors 160 may then be closed. The wing cover nacelles 26 and 28, as presently constructed, are

formed with two degrees of dihedral builtin, and, if

more or less is needed, it can be accomplished with shimming at connecting points of joining assembly 152.

The particular form of construction of hangar 10 enables various alternative and/or adjustment structures which tend to broaden its application. Thus, as will be further described below, the structure can be varied through inclusion of accessory assemblies of relatively easy addition such that the hangars, with but minor variations, will accommodate almost all of the presently existing single engine aircraft in all kinds of weather condition. Further, accessory structures are available which will allow the hangars to accommodate any airplane in the light plane category of conventional design including light twins, with or without wing tip fuel tanks and luggage compartments.

Thus, FIG. 11 illustrates an alternative form of side wall construction for use with low wing monoplanes. The low wing accommodating side walls are constructed in left and right pairs to replace the similar side walls 20 and 22 as constructed in accordance with teachings of FIG. 4. The construction technique is also the same and includes horizontal frame members 182, 184, 186 and 188 as secured by transverse or vertical frame members 190 and suitable X-bracing members 192. Longitudinal strengthening is provided by longitudinal members 194, 196, 198 and 200 as suitably secured to the frame members. The framing is then completely covered over the exterior with integral framing joinder by such as woven rovings impregnated with polyester resin. The cord washers 104 are again utilized to provide uniform seating of the structure. The side walls 180 may then receive the similar roof sections 14 and 16, end wall 24 and wing cover nacelles 26 and 28 to provide cover and protection to a low wing monoplane.

FIGS. 12, 13 and 14 illustrate a hangar center insert structure of standardized form which may be secured longitudinally within hangar 10 to provide shelter for the larger twin engine aircraft. The ridge line insert structure consists of a roof insert 202 and a rear wall insert 204 which simply fastens within the center of hangar 10 as it is separated along the ridge line and rear wall vertical center line. Securing is carried out by suitable fasteners, bolts and the like, and essentially stable structure may be formed without the requirement for additional bracing devices.

The roof center insert 202 is again constructed along lines similar to that for FIGS. 6 and 7 in that it consists of longitudinal frame members 206 joined by a plurality of transverse frame members 208 as suitably secured by a plurality of triangle braces 210. Suitable X- bracing is provided by cross bracing members 212 and, if desired, a ridgeline framing stringer may be included along the peak of roof section 202.

The frame is then covered by suitable application of laminate over the entire exterior surface including integral laminated affixure to individual ones of the framing members, X-bracing etc. In construction, the longitudinal frame members 206 each may be bolted to the ridge frame members 130 of opposite roof sections 14 and 16 to provide an expanded or widened roof covering. In like manner, the rear wall 204 is widened by center insertion of wall structure or end wall portion 204. The construction of end wall portion 204 is again similar to that previously described in that it utilizes vertical frame members 214, base frame member 216 and X-bracing members 218 as bonded to support laminated covering 220. The rear wall portion 204 may be connected in insert between respective half-section rear wall portions 106 (FIG. of rear wall 24.

It is contemplated too that the use of hangars 10 in colder regions will require a forward enclosure 222 as illustrated in FIG. 15. The forward enclosure 222 may be formed with a front panel 224 which may be identical to the rear wall 24 or may be of unitary and lighter construction to enable easy movement during removal of the aircraft. The front panel 224 is rigidly affixed to side panel sections 226 and 228 which are formed to fit securely beneath the outer edge of roof sections 14 and 16 and leading edge of side panels 20 and 22. (See FIGS. 2 and 3). The construction technique utilized for formation of forward enclosure section 222 may be that of conventional framing support and laminated covering procedures, but it is preferable that the formation be easily handled and it may even include wheels, rollers or the like along base contacting portions. A walk-in door may be installed in a suitable cutout between upright framing members of one of the side wall sections 226 or 228, if so desired.

'FIG. 16 illustrates yet another alternative form of enclosure structure which is suitable for use with some aircraft having wing tip gasoline tanks. Thus, a wing cover nacelle 230 is constructed similar to that of wing cover nacelle 28 of FIGS. 9 and 10, except that it includes an outer generally cylindrical portion 232 to receive the wing tip gasoline tank. The wing cover nacelle 230 includes the similar form of joining assembly 152 including upper base flange 162 and an offset lower base flange 164. An upper cover panel 234 is then formed of laminated fiberglas to include the rounded extension 236 of the tank cover portion. In like manner, the laminated lower cover panel 238 includes a curved laminated portion 240 which is suitably secured along a flange connection 242 or the like extending longitudinally at the outer extremity. The wing cover nacelle 230 would also include a front cover (not shown) suitably hinged along lower leading edge spar 244 which may be secured upward against upper leading edge spar 246.

It is also contemplated that even in more temperate weather zones hangar 10 might be reinforced to increase its capability of withstanding relatively higher winds. Thus, additional mooring rings or attachments may be utilized with associated connector cables to provide still greater tie-down strength. Also, and as provided as an accessory device, a set of N-struts may be utilized to re-inforce each of wing cover nacelles 26 and 28 outward from respective side walls 20 and 22 and relative to the ground or cement surface therebeneath.

The foregoing describes a novel hangar assembly for use with small aircraft which is readily transportable and may be utilized with either existing airport tiedown mooring rings or especially placed mooring rings. Such tie-down may be achieved with light tackle, e.g. Va inch wire rope and 5/ l 6 inch turnbuckle, to provide very secure support under all normal weather conditions. In addition, the structure is capable of integral inclusion of additional accessory structures to provide more specialized weather protection in such regions as very cold weather zones, or coastal areas wherein incidence of high winds is increased. Accessory structures are also available which will enable the use of the novel hangar as described herein with all types of light aircraft, mono-plane variety, and nearly all forms of twin engine aircraft.

Changes may be made in the combination and arrangement of elements as heretofore set forth in this specification and shown in the drawings; it being understood that changes may be made in the embodiments disclosed without departing from the spirit and scope of the invention as defined in the following claims.

What is claimed is:

1. A pre-fabricated hangar assembly for sheltering enclosure of an aircraft at a selected ground area, comprising:

a roof section defining parallel longitudinal sides and having at least a rear side formed perpendicular to said longitudinal sides;

left and right side walls each disposed for affixure to respective roof sections longitudinal sides to extend perpendicular to the ground area, each of said side walls having a generally regular cut-out portion along the forward edge;

left and right wing cover nacelles including a joining assembly for secure affixure within respective left and right side wall cut-out portions, said joining assemblies each including an upper base flange for securing on an inner surface of the respective side wall, and an offset lower base flange for securing to an outer surface of the same respective side wall, and further including molded laminer cover sections affixed to said respective joining assemblies at a transverse vertical angle equal to said aircraft wing dihedral angle which cover sections are shaped generally to have a longitudinal crosssectional area similar to said aircraft longitudinal cross-sectional area in order to accommodate the outer wing portions of said aircraft in said closefitting relationship;

a rear wall section formed for affixure to said roof sections and said left and right side walls while contacting the ground area; and

plural tensioning cables connecting each of said left and right walls to the ground area external to said hangar assembly and connecting said rear wall section to said ground area external to said hangar assembly.

2. A hangar assembly as set forth in claim 1 wherein: said roof section, said left and right side walls, said wing cover nacelles and said rear wall section are each individually constructed of lightweight material framing covered by fiberglas laminate.

3. A hangar assembly as set forth in claim 1 which is further characterized to include:

left and right cover panels each hingedly affixed to the forward side of respective left and right wing cover nacelles, said cover panels including means for maintaining the cover panels closed over respective forward sides of the wing cover nacelles.

4. A hangar assembly as set forth in claim 1 wherein said side wall cut-out portions are disposed at a heighth which accommodates high wing monoplanes.

5. A hangar assembly as set forth in claim 4 wherein said side wall cut-out portions are disposed at a heighth which accommodates low wing monoplanes.

6. A hangar assembly as set forth in claim 1 wherein said roof section comprises:

left and right sections of identical structure for joinder along first similar edges to form a roof ridgeline 9 10 while remaining similar and parallel edges consticommodation of a larger aircraft. tute Sald longlmdmal Sldes- 8. A hangar assembly as set forth in claim 1 which is 7. A hangar assembly as set forth in claim 6 which is further characterized to include: l l t bl t bl t a roof insert portion for connection between said first 5 Sal p enslon mg ca es 211:6 e 0 Stansimilar edges of respective left and right portions of dardlzed small arcraft moormg rmgs adjacent each said roof section to expand the transverse dimen- Side Wall and said rear Wall Sectionsion of the hangar assembly thereby to enable acfurther characterized in that: 

1. A pre-fabricated hangar assembly for sheltering enclosure of an aircraft at a selected ground area, comprising: a roof section defining parallel longitudinal sides and having at least a rear side formed perpendicular to said longitudinal sides; left and right side walls each disposed for affixure to respective roof sections longitudinal sides to extend perpendicular to the ground area, each of said side walls having a generally regular cut-out portion along the forward edge; left and right wing cover nacelles including a joining assembly for secure affixure within respective left and right side wall cut-out portions, said joining assemblies each including an upper base flange for securing on an inner surface of the respective side wall, and an offset lower base flange for securing to an outer surface of the same respective side wall, and further including molded laminer cover sections affixed to said respective joining assemblies at a transverse vertical angle equal to said aircraft wing dihedral angle which cover sections are shaped generally to have a longitudinal crosssectional area similar to said aircraft longitudinal crosssectional area in order to accommodate the outer wing portions of said aircraft in said close-fitting relationship; a rear wall section formed for affixure to said roof sections and said left and right side walls while contacting the ground area; and plural tensioning cables connecting each of said left and right walls to the ground area external to said hangar assembly and connecting said rear wall section to said ground area external to said hangar assembly.
 2. A hangar assembly as set forth in claim 1 wherein: said roof section, said left and right side walls, said wing cover nacelles and said rear wall section are each individually constructed of lightweight material framing covered by fiberglas laminate.
 3. A hangar assembly as set forth in claim 1 which is further characterized to include: left and right cover panels each hingedly affixed to the forward side of respective left and right wing cover nacelles, said cover panels including means for maintaining the cover Panels closed over respective forward sides of the wing cover nacelles.
 4. A hangar assembly as set forth in claim 1 wherein said side wall cut-out portions are disposed at a heighth which accommodates high wing monoplanes.
 5. A hangar assembly as set forth in claim 4 wherein said side wall cut-out portions are disposed at a heighth which accommodates low wing monoplanes.
 6. A hangar assembly as set forth in claim 1 wherein said roof section comprises: left and right sections of identical structure for joinder along first similar edges to form a roof ridgeline while remaining similar and parallel edges constitute said longitudinal sides.
 7. A hangar assembly as set forth in claim 6 which is further characterized to include: a roof insert portion for connection between said first similar edges of respective left and right portions of said roof section to expand the transverse dimension of the hangar assembly thereby to enable accommodation of a larger aircraft.
 8. A hangar assembly as set forth in claim 1 which is further characterized in that: said plural tensioning cables are connectable to standardized small aircraft mooring rings adjacent each side wall and said rear wall section. 